Spaceflight turbine pump bearing low-temperature medium simulation test device

Abstract

The invention relates to a space turbine pump bearing low-temperature medium simulation test device, and belongs to the technical field of bearing test devices.The test device divides a test shafting into a low-temperature cooling section and a normal-temperature lubricating section, through the sectional design, the test cost is effectively reduced, and the test efficiency is improved; through a preloading spring and a compensation air inlet structure on the axial loading piston, the loading accuracy of axial force is improved, through the design of an axial guiding linear bearing, the phenomena of low-temperature clamping stagnation and high-speed slipping are prevented, and through the design of an axis liquid inlet flow channel and a spiral auxiliary liquid inlet, an inner ring of a test bearing is effectively cooled, so that the service life of the test bearing is prolonged. By dividing the cooling space in the test cavity, the flowability and cooling efficiency of the cooling medium are effectively improved, and the whole test device has high reliability, stability and safety, is suitable for the simulation test of the low-temperature bearing, and can reduce the test cost and difficulty and improve the test efficiency.

Description

Technical Field

[0001] The invention relates to the field of bearing testing, and in particular to a low-temperature medium simulation test device for aerospace turbopump bearings. Background Art

[0002] The turbopump is the heart of the rocket engine, and the turbopump bearing is the key to the long-term stable operation of the turbopump. The turbopump bearing serves in an ultra-low temperature environment and withstands high-speed and heavy-load conditions. The low-temperature bearing test is an important means to evaluate the performance of bearings in low-temperature environments. It mainly involves tests on the operating stability, friction characteristics, load-bearing capacity and life of bearings under low-temperature conditions. The main purpose is to assess the performance of bearings when loaded and running at high speed in a low-temperature environment, to understand the usage boundaries of the bearings, and to ensure their reliability and durability under specific low-temperature conditions. The existing low-temperature bearing test equipment still has many shortcomings.

[0003] On the one hand, in order to simulate the actual working conditions of low-temperature bearings, the existing technology uses liquid nitrogen as a low-temperature medium for bearing tests, and liquid nitrogen is passed into the entire test cavity for testing; the traditional liquid nitrogen full-area cooling method requires the test tooling to use low-temperature materials (such as bearings and seals) as a whole, which is complex and costly to process, and significantly increases the cost compared to conventional tests; on the other hand, the existing low-temperature test device has an unreasonable design of the cooling medium flow path in the low-temperature cavity, resulting in a large consumption of low-temperature medium, and lacks effective cooling measures for the inner ring of the bearing. When the bearing is in high-speed working conditions, insufficient cooling of the inner ring can easily lead to a temperature increase, causing faults such as burns on the inner ring of the bearing; furthermore, during low-temperature testing, the accuracy of the axial loading force will be affected by many factors such as the temperature and pressure in the cavity, thereby affecting the stability and accuracy of the test.

[0004] In the existing technology, there is a practice of dividing the test chamber into a low-temperature test chamber and a normal-temperature test chamber. The test bearing is in the low-temperature chamber, and the process bearing is in the normal-temperature chamber. This can reduce the test cost and improve the test efficiency to a certain extent. However, the design of the low-temperature cooling chamber in the existing patent is relatively simple, and still does not take into account the cooling problem of the bearing inner ring. The cooling efficiency is relatively low, and it does not consider solving the accuracy problem of the axial loading force. Summary of the Invention

[0005] In response to the shortcomings of the existing technology, the present invention provides a low-temperature medium simulation test device for aerospace turbine pump bearings. By optimizing a series of issues such as the test cavity, axial loading and cooling efficiency, the stability, safety and reliability of the low-temperature test device are effectively improved.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is: A low-temperature medium simulation test device for aerospace turbine pump bearings, comprising a test main shaft, a test bearing, a test companion bearing, a radial loading piston and an axial loading piston, wherein the test companion bearing comprises a radial loading bearing and an axial positioning bearing, the test bearing and the test companion bearing are positioned and installed on the test main shaft to form a test shaft system, the test shaft system is divided into a low-temperature cooling section and a normal temperature lubrication section, the test bearing is located in the low-temperature cooling section, a test cavity shell is provided outside the low-temperature cooling section, the test companion bearing is located in the normal temperature lubrication section, a test companion cavity shell is provided outside the normal temperature lubrication section, the test cavity shell and the test companion cavity shell are sealed and isolated by a sealing assembly, the test bearing is installed in a test bearing seat, an axial loading cover is provided on the left side of the outer ring of the test bearing, an axial guide linear bearing is provided between the axial loading cover and the test bearing seat, the axial loading piston loads the test bearing through the axial loading cover, and a preload spring and a compensating air intake structure are provided on the axial loading piston.

[0007] Furthermore, a plurality of axially guided linear bearings are evenly distributed along the circumference between the axial loading cover and the test bearing seat. The axially guided linear bearings include balls and ball retainers. The ball retainers can distribute and limit the balls. Corresponding ball grooves are provided between the axial loading cover and the test bearing seat. The balls are installed and retained in the ball grooves by the ball retainers.

[0008] Furthermore, the inner side surface of the test bearing seat and the outer side surface of the axial loading cover are designed to be parallel conical surfaces, with the conical surface larger on the left and smaller on the right, and the angle of the conical surface is set according to actual needs.

[0009] Furthermore, a plurality of rectangular grooves are evenly distributed along the circumferential direction on the end surface of the axial loading cover in contact with the outer ring of the test bearing, so as to increase the friction between the axial loading cover and the outer ring of the test bearing.

[0010] Furthermore, the axial loading piston is installed on the left shell end cover of the test chamber shell through the axial piston mounting seat. The axial loading piston is provided with a retaining ring, which divides the axial piston mounting seat into a left chamber and a right chamber. The left chamber is provided with a preload spring and a compensation air inlet, and the right chamber is provided with an air outlet.

[0011] Furthermore, the test bearing is installed at the left end of the test spindle, and a test bearing inner ring pressure cover is provided on the left side of the test bearing. The test bearing inner ring pressure cover is fixed on the end face of the test spindle, and an axial liquid inlet channel and an axial liquid outlet nozzle are provided at the left end of the test spindle. The axial liquid inlet channel is a blind hole arranged at the axis of the left end of the test spindle, and the axial liquid outlet nozzle is located on the right side of the test bearing and extends radially along the test spindle, with one end connected to the axial liquid inlet channel and the other end connected to the outside of the test spindle. An axial liquid inlet connected to the axial liquid inlet channel is provided in the middle of the test bearing inner ring pressure cover.

[0012] Furthermore, the axial liquid inlet is a spiral auxiliary liquid inlet, which is formed by setting an inner hole in the middle of the test bearing inner ring pressure cover and setting a spiral groove on the wall of the inner hole.

[0013] Furthermore, the test chamber shell is provided with a liquid inlet and a liquid outlet for the cooling medium to enter and exit, the test bearing seat divides the interior of the test chamber shell into a left test chamber and a right test chamber, and a sealing ring mounting seat is provided between the test bearing seat and the left shell end cover. The sealing ring mounting seat divides the left test chamber into a liquid inlet space and a liquid outlet space, the liquid inlet is connected to the liquid inlet space, and the liquid outlet is connected to the liquid outlet space.

[0014] Furthermore, a plurality of groups of cross-flow channels are provided on the test cavity shell outside the test bearing seat, and the flow channels connect the liquid inlet space of the left test cavity and the right test cavity for the cooling medium to pass through.

[0015] Furthermore, the test bearing seat is installed and fixed on the test chamber shell through the left side pressure cover of the bearing seat and the right side pressure cover of the bearing seat. A sealing ring is provided between the left side pressure cover of the bearing seat and the sealing ring mounting seat. A flow channel hole extending axially is provided on the bearing seat, and the flow channel hole connects the liquid inlet space of the left test chamber and the right test chamber.

[0016] Beneficial effects: The present invention adopts the segmented design of the normal temperature lubrication section and the low temperature cooling section, so that only the low temperature test section components need to be replaced for each test, reducing material costs and processing difficulty. The normal temperature oil lubrication section can be designed with a margin, and by increasing the redundancy of the normal temperature section such as the speed, load, and life, it is ensured that the low temperature test tooling can operate stably under various low temperature test bearing working conditions, thereby improving the reliability, safety and adaptability of the entire test tooling.

[0017] The present invention reduces the inaccurate axial loading force of the test bearing caused by low-temperature sticking, and even the no-load high-speed slippage of the bearing caused by the axial force being "0" through the design of the test bearing axial guide linear bearing, thereby improving loading reliability; at the same time, the axial loading cover and the test bearing seat are designed as conical surfaces, which effectively compensates for the uneven axial shrinkage problem caused by temperature difference, prevents unbalanced loading, and improves loading smoothness; the present invention also avoids the reverse axial force of the piston caused by the liquid nitrogen pressure in the low-temperature test chamber through the design of the axial loading preload spring and the compensation air intake, thereby improving the loading accuracy of the axial force of the test bearing.

[0018] The present invention improves the cooling condition of the inner ring of the test bearing through the spiral auxiliary liquid inlet designed on the inner ring pressure cover of the test bearing and the liquid inlet channel and liquid outlet nozzle of the test axis, effectively reduces the temperature of the inner ring of the test bearing, and prevents the inner ring of the bearing from burning due to insufficient cooling capacity under high-speed working conditions of the bearing; the low-temperature test chamber of the present invention is designed with horizontal and vertical cross flow channels on the shell, so that the cooling medium can cool the shell, ensuring a low-temperature environment inside the entire test chamber, and a flow channel hole is provided on the test bearing seat. The cooling medium flows to the test bearing after passing through the flow channel hole, which can fully cool the outer ring; the above design enables the cooling medium to achieve sufficient circulation in the test chamber, achieve a higher cooling effect on both the outer ring and the inner ring of the test bearing, and can improve the cooling efficiency, reduce the cooling medium consumption, and reduce the test cost.

[0019] The bearing low-temperature medium simulation test device of the present invention can not only be applied to aerospace turbopump bearings, but can also be widely used in the low-temperature bearing test industry, effectively reducing test costs and difficulty and improving test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall cross-sectional structure of the test device of the present invention; Figure 2 It is a structural schematic diagram of the test shaft system of the present invention; Figure 3 Schematic diagram of the structure of the axial guide linear bearing of the present invention, (wherein, Figure 3 (a) Figure 3 (b) NN-direction cross-sectional view); Figure 4 is a schematic diagram of the structure of the axially loaded gland, (where Figure 4 (a) Figure 4 (b) right side view); Figure 5 yes Figure 1 Schematic diagram of the local structure at A in the middle; Figure 6 yes Figure 1 Schematic diagram of the local structure at point B.

[0021] Figure numerals: 01 coupling, 02 test bearing inner ring gland, 03 right housing end cover, 04 test chamber housing, 05 axial locating bearing, 06 test bearing step spacer, 07 radially loaded bearing outer ring gland, 08 radially loaded bearing outer ring spacer, 09 radially loaded bearing, 10 radially loaded piston, 11 test bearing radial bearing body, 12 test bearing air seal gland, 13 middle sealing baffle, 14 sealing carbon ring, 15 bearing seat right side gland, 16 test chamber housing, 17 test bearing seat, 18 bearing seat left side gland, 19 liquid inlet, 2 0 Left side housing end cover, 21 sealing ring mounting seat, 22 axial piston sealing ring baffle, 23 axial piston mounting seat, 24 axial loading piston, 241 baffle ring, 242 compensation air inlet, 243 air outlet, 25 preload spring, 26 liquid outlet, 27 axial loading pressure cover, 28 axial guide linear bearing, 281 ball, 282 ball cage, 283 ball groove, 284 rectangular groove, 29 test bearing, 30 test spindle, 31 test bearing inner ring pressure cover, 32 axial liquid inlet channel, 33 axial liquid outlet nozzle, 34 spiral auxiliary liquid inlet. DETAILED DESCRIPTION

[0022] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, in the present invention, the directions or positional relationships indicated by terms such as "upper", "lower", "front", "back", "left", "right", "inside", and "outside" are relative directions or positional relationships based on the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or component referred to must have a specific direction.

[0023] like Figure 1 As shown, the present invention provides a low-temperature medium simulation test device for aerospace turbine pump bearings, the test device includes a test spindle 30, a test bearing 29, a test companion bearing, a radial loading piston 10 and an axial loading piston 24, the test bearing 29 is a low-temperature bearing, in this embodiment, the test bearing 29 is an aerospace turbine pump bearing, the test companion bearing includes a radial loading bearing 09 and an axial positioning bearing 05, each bearing is positioned and installed on the test spindle 30 to form a test shaft system, the test shaft system is divided into a low-temperature cooling section and a normal temperature lubrication section, the test bearing 29 is located in the low-temperature cooling section, the low-temperature cooling section A test chamber shell 16 is provided on the outside to form a low-temperature test chamber, and the test bearing is located in the normal temperature lubrication section. A test chamber shell 04 is provided on the outside of the normal temperature lubrication section to form a normal temperature lubrication chamber. The test chamber shell 16 and the test chamber shell 04 are sealed and isolated by a sealing assembly; the test chamber shell 16 is provided with a liquid inlet 19 and a liquid outlet 26 for the cooling medium, and the cooling medium enters the low-temperature test chamber through the liquid inlet 19, circulates in the low-temperature test chamber, and is discharged through the liquid outlet 26. The normal temperature test chamber shell 16 is provided with an oil supply port and an oil return port for realizing normal temperature lubrication of the normal temperature lubrication section.

[0024] based on Figure 1-2 In the orientation shown, on the test shaft system, the test bearing 29 is installed at the left end of the test main shaft 30, located in the low-temperature cooling section, a test bearing seat 17 is provided on the outside of the test bearing 29, the test bearing seat 17 is fixedly connected to the test chamber housing 16, a test bearing inner ring pressure cover 31 and an axial loading pressure cover 27 are provided at the left end of the test bearing 29, and the axial loading piston 24 axially loads the test bearing 29 through the axial loading pressure cover 27; the right side of the test bearing 29 is positioned by a shaft shoulder, and the accompanying test bearing is installed at the right end of the test main shaft 30, located in the normal temperature lubrication section, the accompanying test bearing includes a radial loading bearing 09 and an axial locating bearing 05, the radial loading bearing 09 is located on the left side of the axial locating bearing 05, the radial loading bearing 09 includes a pair of bearings, which are separated by an inner ring spacer and a radial loading bearing outer ring spacer 08, and the radial A test bearing radial carrier 11 is provided to the outside of the loading bearing 09, and the radial loading piston 10 loads the radial loading bearing 09 through the test bearing radial carrier 11; the left side of the radial loading bearing 09 is positioned by the step on the test main shaft 30, and the right side is provided with a test bearing step spacer 06 and a radial loading bearing outer ring pressure cover 07, the right side of the test bearing step spacer 06 is the axial locating bearing 05, the outer ring of the axial locating bearing 05 cooperates with the test cavity housing 04, the right side of the axial locating bearing 05 is provided with a test bearing inner ring pressure cover 02 and a right side housing end cover 03, the right side of the housing end cover 03 is fixed to the test cavity housing 04 by screws and is sealed with the test bearing inner ring pressure cover 02 by threads, the right side housing end cover 03 is also provided with an oil supply port and an oil supply channel, and the right side of the test main shaft 30 is connected with a coupling 01.

[0025] like Figure 1 and 5 As shown, the left end of the test chamber housing 16 is provided with a left housing end cover 20, and the axial loading piston 24 is installed on the left housing end cover 20 through an axial piston mounting seat 23. The axial piston mounting seat 23 is located on the outside of the left housing end cover 20. Two sealing rings are provided between the axial loading piston 24 and the left housing end cover 20. An axial piston sealing ring baffle 22 is provided on the inner side of the left housing end cover 20. The right side of the axial loading piston 24 presses against the axial loading pressure cover 27. The axial loading piston 24 is provided with a baffle ring 241. The baffle ring 241 divides the interior of the axial piston mounting seat 23 into two chambers, left and right. A preload spring 25 is provided in the left chamber and a compensation air inlet 242 is opened. An air outlet 243 is provided on the right chamber. The preload spring 25 provides a certain axial thrust for the piston rod. When axial loading is performed, air can also be inflated into the left chamber through the compensation air inlet 242 to compensate for the reverse thrust of the liquid nitrogen pressure in the low-temperature test chamber on the axial loading piston 24, thereby improving the accuracy of the axial loading force of the test bearing 29 and improving the test stability.

[0026] like Figure 1 As shown, the test bearing 29 is arranged in the test chamber shell 16 through the test bearing seat 17. The left and right ends of the test bearing seat 17 are respectively provided with a bearing seat left pressure cover 18 and a bearing seat right pressure cover 15. The bearing seat left pressure cover 18 and the bearing seat right pressure cover 15 are respectively connected to the test chamber shell 16 by screws, thereby fixing the test bearing seat 17 on the test chamber shell 16. The axial loading pressure cover 27 is located in the test bearing seat 17. The right end of the axial loading pressure cover 27 contacts the outer ring of the test bearing 29 for transmitting axial loading force. An axial guide linear bearing 28 is provided between the axial loading pressure cover 27 and the test bearing seat 17.

[0027] like Figure 3-4 As shown, the axial guide linear bearing 28 includes balls 281 and ball retainers 282. The balls 281 are distributed along the axial direction. The ball retainers 282 are used to distribute and limit the balls 281. The axial loading cover 27 and the test bearing seat 17 are provided with corresponding ball grooves 283. The balls 281 are installed and retained in the ball grooves 283 through the ball retainers 282, which can guide the axial loading and prevent the axial loading cover 27 from rotating during operation. At the same time, it also avoids the outer ring of the test bearing 29 from rotating. Figure 3 In the illustrated embodiment, a total of eight axial guide linear bearings 28 are designed between the axial loading cover 27 and the test bearing seat 17 , and the eight axial guide linear bearings 28 are evenly distributed along the circumferential direction.

[0028] Furthermore, the inner side surface of the test bearing seat 17 and the outer side surface of the axial loading cover 27 are designed to be parallel to each other. The cone surface is larger on the left and smaller on the right. The specific cone surface angle is set according to actual needs to prevent unbalanced loading or jamming caused by uneven temperature of the bearing seat; in this embodiment, the cone surface angle is 1°. Specifically, during the test, due to the high-speed rotation of the test bearing 29, the temperature rises, and the temperature of the test bearing seat 17 on the side close to the test bearing 29 is higher than the temperature on the axial loading side, which makes the test bearing seat 17 and the axial loading cover 27 shrink at different locations along the axial direction. If it is a conventional cylindrical surface design, the shrinkage of the inner hole of the test bearing seat 17 is different at different locations along the axial direction, and the shrinkage is larger on the side close to the axial loading piston 24, and smaller on the side close to the test bearing 29, which will cause the axial loading cover 27 to tilt, and ultimately lead to axial load eccentricity. After the present invention designs the mating surfaces of the two as conical surfaces, it can compensate for the different shrinkages on the left and right sides of the axial loading cover 27, so that within the normal temperature difference range of the test chamber, the axial loading cover 27 and the center line of the shaft can maintain good coaxiality to avoid the occurrence of eccentricity.

[0029] In addition, if Figure 4As shown, a plurality of rectangular grooves 284 are evenly distributed along the circumferential direction on the end face where the axial loading cover 27 contacts the outer ring of the test bearing 29. During the loading process, the presence of the rectangular grooves 284 can increase the friction between the axial loading cover 27 and the outer ring of the test bearing 29, thereby preventing the outer ring of the bearing from rotating and causing a running ring failure.

[0030] As shown in Figure 1, in the low-temperature test chamber, the test bearing seat 17 divides the interior of the low-temperature test chamber into a left test chamber and a right test chamber, and a sealing ring mounting seat 21 is provided between the left side pressure cover 18 of the bearing seat and the left side shell end cover 20. The sealing ring mounting seat 21 divides the left side test chamber into a liquid inlet space and a liquid outlet space; specifically, the left side of the sealing ring mounting seat 21 is connected to the left side shell end cover 20 by screws, and the right side is sealed with the left side pressure cover 18 of the bearing seat by a sealing ring. The middle part of the sealing ring mounting seat 21 is opened, and the axial loading piston 24 passes through the opening and rests on the axial loading cover 27. The liquid outlet 26 is provided on the left shell end cover 20 and is communicated with the liquid outlet space inside the sealing ring mounting seat 21. The liquid inlet 19 is provided on the left end face of the test chamber shell 16 and is communicated with the liquid inlet space outside the sealing ring mounting seat 21. The sealing ring mounting seat 21 divides the liquid inlet 19 and the liquid outlet 26 into different areas, so that the cooling medium entering the liquid inlet 19 will not flow directly to the liquid outlet 26, but will flow out from the liquid outlet 26 after cooling flow and circulation in the test chamber.

[0031] There are multiple liquid inlets 19 and liquid outlets 26, which are evenly distributed along the circumference. The circumference of the liquid outlet 26 is located inside the circumference of the liquid inlet 19. In a specific embodiment, there are three liquid inlets 19 and three liquid outlets 26.

[0032] The test chamber shell 16 adopts a thick-walled shell and is provided with multiple groups of horizontal and vertical cross flow channels on the shell. The cooling medium flows in the flow channels, which can reduce the temperature of the test chamber shell 16. In addition, the thick-walled design can form a good insulation effect for the entire test chamber. The flow channels on the test chamber shell 16 correspond to the liquid inlet 19, and three groups are provided.

[0033] The flow channel on the test chamber shell 16 connects the left test chamber and the right test chamber. At the same time, the test bearing seat 17 is provided with a plurality of flow channel holes extending in the axial direction. The left pressure cover 18 of the bearing seat and the right pressure cover 15 of the bearing seat are also provided with corresponding through holes. The cooling medium enters the left test chamber from the liquid inlet 19. A part of it enters the right test chamber after passing through the flow channel on the test chamber shell 16, which can cool the test chamber shell 16 and ensure the overall low temperature environment inside the shell. The other part enters the right test chamber through the flow channel hole on the test bearing seat 17, which can realize the cooling of the test bearing seat 17 and the outer ring of the test bearing 29. The cooling medium in the right test chamber enters the internal space of the axial loading pressure cover 27 through the test bearing 29, so that the test bearing 29 located inside the axial loading pressure cover 27 is completely immersed in the low-temperature medium. A through hole is provided on the left end face of the axial loading pressure cover 27. The cooling medium passes through the through holes on the axial loading pressure cover 27 and the sealing ring mounting seat 21, enters the sealing ring mounting seat 21, and finally flows out from the liquid outlet 26, realizing a large circulation of the cooling medium in the test chamber.

[0034] like Figure 1 and Figure 6 As shown, further, in order to improve the cooling effect at the axis, the present invention is provided with an axis liquid inlet channel 32 and an axis liquid outlet nozzle 33 at the left end of the test spindle 30, which facilitates the cooling medium to enter the axis to cool the inner ring of the test bearing 29. The axis liquid inlet channel 32 is a blind hole provided at the axis of the left end of the test spindle 30, and the axis liquid outlet nozzle 33 is located on the right side of the test bearing 29. The axis liquid outlet nozzle 33 extends along the radial direction of the test spindle 30, one end of which is connected to the axis liquid inlet channel 32, and the other end of which is connected to the right test cavity on the right side of the test bearing 29. In order to improve the fluidity of the cooling medium, a shaft is provided in the middle of the test bearing inner ring pressure cover 31. The spiral auxiliary liquid inlet 34 connected to the liquid inlet channel 32 is formed by setting an inner hole on the test bearing inner ring cover 31 and setting a spiral groove on the inner hole wall. The spiral auxiliary liquid inlet 34 plays a drainage role during the test process, and can drive the cooling medium to enter the axial liquid inlet channel 32 in a flowing state, thereby improving the fluidity of the cooling medium. The cooling medium entering the axial liquid inlet channel 32 flows out from the axial liquid outlet nozzle 33 to the right test cavity on the right side of the test bearing 29, forming a small circulation at the inner ring of the test bearing 29, effectively reducing the temperature of the inner ring of the bearing, and preventing the inner ring of the bearing from burning due to insufficient cooling capacity under high-speed working conditions.

[0035] The test device designed in the present invention has a cooling medium with strong fluidity and high utilization efficiency in the test chamber. The thick-wall design and flow channel design of the test chamber shell 16 improve the thermal insulation effect and ensure the low temperature environment of the entire test chamber. The design of the flow channel holes on the test bearing seat 17 and the axial flow channel holes on the test spindle 30 enables the cooling medium to effectively cool the outer ring and inner ring of the test bearing 29. The cooling medium forms a large circulation and a small circulation in the test chamber with high cooling efficiency, which can achieve a sufficient cooling effect and ensure the safety of the test under high-speed rotation. At the same time, the utilization rate of the cooling medium is improved and the consumption of the cooling medium is reduced.

[0036] The test chamber housing 16 of the present invention and the accompanying test chamber housing 04 are sealed and isolated by a sealing assembly, which includes a central sealing baffle 13, a sealing carbon ring 14, and an airtight sealing cover 12. The accompanying test chamber housing 04 and the test chamber housing 16 are connected by screws. The central sealing baffle 13 is fixed to the right end of the test chamber housing 16 by screws and a sealing ring is installed on the contact surface between the two. The central sealing baffle 13 is located between the test chamber housing 16 and the accompanying test chamber housing 04, which can separate the test chamber housing 16 and the accompanying test chamber housing. 04 is isolated from the cavity inside, and an inner hole is provided on the middle sealing baffle 13. A plurality of sealing carbon rings 14 are installed between the inner hole of the middle sealing baffle 13 and the outer diameter of the test spindle 30. The airtight sealing cover 12 is located in the test cavity shell 04 and is installed on the test spindle 30 on the left side of the test bearing. The airtight sealing cover 12 can pass compressed air to form an air film at the gap to seal the gap on the test spindle 30, thereby achieving a sealing effect and preventing the media in the cavities on both sides from communicating with each other. The sealing component used in the present invention has a simple structure and a good sealing effect.

[0037] The above description is merely a preferred embodiment of the present invention and does not constitute any form of limitation to the present invention. Although the present invention has been disclosed as a preferred embodiment as above, it is not intended to limit the present invention. Any technician familiar with the present profession can make some changes or modifications to equivalent embodiments of equivalent changes using the technical content disclosed above without departing from the scope of the technical solution of the present invention. However, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. A low-temperature medium simulation test device for aerospace turbopump bearings, comprising a test spindle, a test bearing, a companion test bearing, a radial loading piston, and an axial loading piston. The companion test bearing comprises a radial loading bearing and an axial positioning bearing. The test bearing and the companion test bearing are positioned and mounted on the test spindle to form a test shaft system. The device is characterized in that: The test shaft system is divided into a low-temperature cooling section and a normal temperature lubrication section. The test bearing is located in the low-temperature cooling section. A test cavity shell is provided outside the low-temperature cooling section. The accompanying test bearing is located in the normal temperature lubrication section. A accompanying test cavity shell is provided outside the normal temperature lubrication section. The test cavity shell and the accompanying test cavity shell are sealed and isolated by a sealing assembly. The test bearing is installed in a test bearing seat. An axial loading cover is provided on the left side of the outer ring of the test bearing. An axial guide linear bearing is provided between the axial loading cover and the test bearing seat. The axial loading piston loads the test bearing through the axial loading cover. The axial loading piston is provided with a preload spring and a compensation air intake structure.

2. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 1, characterized in that: A plurality of axially guided linear bearings are evenly distributed along the circumference between the axial loading cover and the test bearing seat. The axially guided linear bearings include balls and ball retainers. The ball retainers can distribute and limit the balls. Corresponding ball grooves are provided between the axial loading cover and the test bearing seat. The balls are installed and retained in the ball grooves by the ball retainers.

3. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 2, characterized in that: The inner side surface of the test bearing seat and the outer side surface of the axial loading cover are designed to be parallel conical surfaces. The conical surface is larger on the left and smaller on the right, and the angle of the conical surface is set according to actual needs.

4. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 2, characterized in that: A plurality of rectangular grooves are evenly distributed along the circumference on the end surface where the axial loading cover contacts the outer ring of the test bearing, so as to increase the friction between the axial loading cover and the outer ring of the test bearing.

5. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 1, characterized in that: The axial loading piston is installed on the left shell end cover of the test chamber shell through the axial piston mounting seat. The axial loading piston is provided with a retaining ring, which divides the axial piston mounting seat into a left chamber and a right chamber. The left chamber is provided with a preload spring and a compensation air inlet, and the right chamber is provided with an air outlet.

6. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 1, characterized in that: The test bearing is installed on the left end of the test spindle, and a test bearing inner ring pressure cover is provided on the left side of the test bearing. The test bearing inner ring pressure cover is fixed on the end face of the test spindle. An axial liquid inlet channel and an axial liquid outlet nozzle are provided at the left end of the test spindle. The axial liquid inlet channel is a blind hole arranged at the axis of the left end of the test spindle. The axial liquid outlet nozzle is located on the right side of the test bearing and extends radially along the test spindle. One end is connected to the axial liquid inlet channel, and the other end is connected to the outside of the test spindle. An axial liquid inlet connected to the axial liquid inlet channel is provided in the middle of the test bearing inner ring pressure cover.

7. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 6, characterized in that: The axial liquid inlet is a spiral auxiliary liquid inlet, which is formed by arranging an inner hole in the middle of the test bearing inner ring pressure cover and arranging a spiral groove on the wall of the inner hole.

8. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 1, characterized in that: The test chamber shell is provided with a liquid inlet and a liquid outlet for the cooling medium to enter and exit. The test bearing seat divides the interior of the test chamber shell into a left test chamber and a right test chamber. A sealing ring mounting seat is provided between the test bearing seat and the left shell end cover. The sealing ring mounting seat divides the left test chamber into a liquid inlet space and a liquid outlet space. The liquid inlet is connected to the liquid inlet space, and the liquid outlet is connected to the liquid outlet space.

9. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 8, characterized in that: A plurality of groups of cross-flow channels are provided on the test cavity shell outside the test bearing seat. The flow channels connect the liquid inlet space of the left test cavity and the right test cavity for the cooling medium to pass through.

10. The low temperature medium simulation test device for aerospace turbopump bearings according to claim 8, characterized in that: The test bearing seat is fixed on the test chamber housing through the left side pressure cover of the bearing seat and the right side pressure cover of the bearing seat. A sealing ring is provided between the left side pressure cover of the bearing seat and the sealing ring mounting seat. A flow channel hole extending axially is provided on the bearing seat, and the flow channel hole connects the liquid inlet space of the left test chamber and the right test chamber.

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